Orbit debris removal and asset protection assembly

ABSTRACT

An orbital debris removal assembly is provided. The orbital debris removal and asset protection assembly includes a plurality of spaced layers of netting. Each netting layer includes a plurality of sub-layers of meshed composite fibers that are configured and arranged to break up debris that comes in contact with the assembly.

BACKGROUND

Objects that are in orbit around the earth as the result of space initiatives that no longer serve any function are called orbital debris. Examples of orbital debris include spacecraft, upper stages of launch vehicles, debris released during spacecraft separation from its launch vehicle or during mission operations, debris created as a result of spacecraft or upper stage explosions or collisions, solid rocket motor effluents, paint flecks and thermal blankets. Most of the orbital debris is concentrated in what is considered low earth orbits. This orbital debris poses an increasing risk to functioning spacecraft.

It is currently estimated that the orbital debris includes approximately 19,000 objects that are greater than 10 cm in diameter, approximately 500,000 objects that are greater than 1 cm and tens of millions of objects that are smaller than 1 cm. The impact speed of orbital debris on a spacecraft is typically around 10 Km/sec. At this impact speed, objects greater than 1 cm can cause a catastrophic failure to a spacecraft while objects that are less than 1 cm can still cause significant damage. Objects that are greater than 10 cm are tracked by U.S. Space Surveillance Network. Based on the tracking, spacecraft are maneuvered around these relatively large objects. In most situations a protective covering (shield) on the spacecraft can deal with objects less than 3 mm. However, for objects having a diameter greater than 3 mm and less than 10 cm and effective protection mechanism is not currently available.

For the reasons stated above and for other reasons stated below which will become apparent to those skilled in the art upon reading and understanding the present specification, there is a need in the art for an apparatus and method of dealing with orbital debris between 3 mm to 10 cm diameter.

SUMMARY OF INVENTION

The above-mentioned problems of current systems are addressed by embodiments of the present invention and will be understood by reading and studying the following specification. The following summary is made by way of examples and not by way of limitations. The summary is merely provided to aid the reader in understanding some of the aspects of the invention.

In one embodiment, an orbital debris removal assembly is provided. The orbital removal assembly in this embodiment includes a plurality of spaced layers of netting. Each netting layer includes sub-layers of meshed composite fibers configured and arranged to break up debris that comes in contact with the assembly.

In another embodiment example, another orbital debris removal assembly is provided. This orbital debris removal assembly includes a plurality of spaced layers of netting formed in at least, a partial sphere shape. Each netting layer includes meshed composite fibers. The plurality of spaced layers of netting having an outer layer, an inner layer and at least one mid layer between the outer layer and the inner layer. Each layer having a select fiber density, the fiber density of the meshed composite fibers in each spaced layer varying from the outer layer to the inner layer.

In still another example embodiment, another orbital debris removal assembly is provided. The orbital debris removal assembly includes a spacecraft and a plurality of spaced netting layers. The spacecraft is configured to navigate in space. The plurality of spaced netting layers are coupled to the spacecraft. Each netting layer includes meshed fibers.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention can be more easily understood and further advantages and uses thereof will be more readily apparent, when considered in view of the detailed description and the following figures in which:

FIG. 1 is an illustration of an orbital debris removal assembly of one embodiment of the present invention;

FIG. 2A is an illustration of the orbital debris removal assembly of FIG. 1 in a non-deployed configuration;

FIG. 2B is an illustration of the orbital debris removal assembly of FIG. 1 in a partial deployed configuration;

FIG. 2C is an illustration of the orbital debris removal assembly of FIG. 1 in a fully deployed configuration;

FIG. 3 is a block diagram of the orbital debris removal assembly of FIG. 1 in a non-deployed configuration;

FIG. 4 is an illustration of the orbital debris removal assembly of FIG. 1 in a partially deployed configuration, positioned to protect a satellite;

FIG. 5 is an illustration of a plurality of layers of netting of one embodiment of the present invention;

FIG. 6 is an illustration of debris engaging the plurality of layers of netting in one embodiment of the present invention;

FIG. 7 is a side view illustration of sub-layers of the layers of netting of one embodiment of the present invention;

FIG. 8 is an illustration of a sub-layer in one embodiment of the present invention; and

FIG. 9 is an illustration of meshed netting used to form a sub-layer in one embodiment of the present invention.

In accordance with common practice, the various described features are not drawn to scale but are drawn to emphasize specific features relevant to the present invention. Reference characters denote like elements throughout Figures and text.

DETAILED DESCRIPTION

In the following detailed description, reference is made to the accompanying drawings, which form a part hereof, and in which is shown by way of illustration specific embodiments in which the inventions may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention, and it is to be understood that other embodiments may be utilized and that changes may be made without departing from the spirit and scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present invention is defined only by the claims and equivalents thereof.

Embodiments of the present invention provide an orbital debris removal and asset protection assembly (an orbital debris removal assembly) that effectively deals with space debris. Moreover, embodiments provide a passive impact destruction assembly as opposed to some sort of space weapon thus making its use more acceptable by the international space community. Embodiments use the energy produced by high velocity debris particles against themselves to breakup and create shield-able size particles. In embodiments, a multi-layer critical spaced netting assembly is provided. In one embodiment, the assembly is deployable in an aerospace structure frame that is generally in the shape of a sphere or partial sphere as discussed below. In other embodiments other shapes of the assembly of multi-layer critical spaced netting are used. Moreover, in one embodiment a shape that lends itself to an effective employment is used. The orbital debris removal assembly acts to intercept and pulverize space debris. In one embodiment, the orbital debris removal assembly is designed to be deployed around a critical asset to intercept and pulverize debris. In another embodiment the orbital debris removal assembly is set to roam in space sweeping out and destroying orbital debris.

Each layer of meshed netting of the orbital debris removal assembly includes a mesh density. The mesh density in each layer, in an embodiment, is increased to insure that all the particles sizes of interest will intersect with one of the net layers and the resulting small particles will intersect with further inner netting layers. In embodiments, the wire fiber or fiber thickness of the netting in each layer is sized to ensure the breakup of the incident particle into smaller particles. The multiple mesh layers take advantage of the fact that multiple wired layers are much more efficient on the total areal density basis than an equivalent areal density of a single layer. In addition, the design of the orbital debris removal assembly has an additional feature that allows the probability that a critical fission like effect can be generated wherein multiple debris particles (and within each impact debris particle itself) are generated upon impact with outer mesh layers interacting with incoming debris particles in interior mesh layers causing a cascading impact set of events where the particles will continuously be broken into smaller particles while inside or in the neighborhood of the orbital debris removal assembly. In some embodiments, composite such as, but not limited to, Dyneema fiber bundles are used to form the meshed netting. In other embodiments metal or ceramic fibers are used. The use of composite fibers allows for a savings in mass of 60% over a metal wire configuration.

Referring to FIG. 1, in an embodiment of an orbital debris removal assembly 100 is illustrated. In particular, the orbital debris removal assembly 100 is illustrated in space 102 orbiting the earth 104. Debris 106 is also illustrated in space 102. Further illustrated is the debris 106 a engaging (impacting) the orbital debris removal assembly 100 and residue (or shieldable) debris 106 b that has been intercepted and pulverized by the orbital debris removal assembly 100. FIG. 2A illustrates the orbital debris removal assembly 100 of an embodiment. In particular, FIG. 2A illustrates a spacecraft 110 having deployed booms 112 a and 112 b and thrusters 114 a and 114 b. The thrusters 114 a and 114 b are used to position the spacecraft 110 in a desired location in space. The orbital debris removal assembly 100 in this embodiment includes a first section of the orbital debris removal assembly 100 a and a second section of the orbital debris removal assembly 100 b that are in a non-deployed (stowed) configuration.

As stated above, the first section 100 a and second section 100 b are in a non-deployed configuration in FIG. 2A. Referring to FIG. 2B, the second section of the orbital debris removal assembly 100 b is illustrated in a deployed configuration. This illustration further provides an understanding of the formation of the orbital debris removal assembly 100 in one embodiment. As illustrated, this second section of the orbital debris removal assembly 100 b includes a plurality of frame members 120 that form layers of netting 220 a, 220 b, 220 c, 220 d, and 220 e. Although the illustration shows five layers of netting 220 a, 220 b, 220 c, 220 d and 220 e, it will be understood that other numbers of layers can be used depending on the application (i.e. size of objects to breakup, density of mesh netting, diameter size of fibers used, etc.) The frame members 120 are further illustrated as forming a first netting support frame 200 a for the first layer of netting 220 a, a second netting support frame 200 b for the second layer of netting 220 b, a third netting support layer 200 c for the third layer of netting 220 c, a fourth netting support frame 200 d for the fourth layer of netting 220 d, and a fifth netting support frame 200 e for the fifth layer of netting 220 e. As illustrated, the netting layers 220 a-220 e include an outer layer 220 a and an inner layer 220 e and in this embodiment, a plurality of mid-layers 220 b-200 d.

Referring to FIG. 2C, an illustration of the orbital debris removal assembly 100 having both the first section 100 a and second section 100 b deployed is provided. In this embodiment, the spacecraft 110 is totally encased by the spherically shaped netting layers 220 a through 220 e. Hence in this embodiment, the spacecraft 110 is protected from all directions with the spherically shaped netting. One benefit of having the netting layers 220 a-220 e in at least a partial spherical shape is that there is no special pointing (positioning) requirements of the spacecraft 110 needed during the interception of the debris 106. The overall diameter of the orbital debris removal assembly 100 is selected based on a desired area to be covered and application. Hence any diameter is contemplated. An example diameter of the orbital debris removal assembly 100 is approximately between 10 to 30 meters.

FIG. 3 illustrates a block diagram of an embodiment of the orbital debris removal assembly 100. As illustrated, the spacecraft 110 in this embodiment includes a controller 250 and a transceiver 254. The transceiver is in communication with the controller 250. The transceiver 254 receives instructions from a transmitter on earth (not shown). Based on the instructions received, the controller 250 positions the spacecraft 110 with the first and second thrusters 114 a and 114 b. The controller 250 is further coupled to control deploying assemblies 252 a and 252 b. The deploying assemblies 252 a and 252 b are designed to deploy the respective first and second sections 100 a and 100 b of the orbital debris removal assembly 100. In one embodiment, the deploying assemblies 252 a and 252 b are inflatable members. In another embodiment, the deploying assemblies 252 a and 252 are activation arms that are designed to selectively deploy and retract the sections 100 a and 100 b of the orbital debris removal assembly 100. In embodiments, the netting layers 220 a-220 e can remain in a stored configuration in orbit for future use to prevent catastrophic collisions with an asset or spacecraft 110.

The orbital debris removal assembly 100 of FIG. 3 includes sensors 260 and 262. In one embodiment sensor 260 is an impact sensor that is in communication with the controller 250. The impact sensor 260 senses impact of debris on the orbital debris removal assembly 100. The controller 250 tracks the number of the impacts the orbital debris removal assembly 100 has taken and relays the information to a control station on earth via transceiver 254 in one embodiment. This information can then be used to determine when the orbital debris removal assembly 100 should be replaced. Hence, a maximum number of impacts can be set to indicate replacement of the orbital debris removal assembly 100. In one embodiment, sensor 262 is a velocity sensor 262 that is also in communication with the controller 250. The velocity sensor 262 senses earth directed velocity components of fractured debris. This information would be used to support additional operational guidelines of the orbital debris removal assembly 100.

FIG. 4 illustrates another method of deploying an orbital removal assembly 100 of an embodiment. As illustrated in this deployment, a first section 100 a of an orbital removal assembly 100 is deployed to form partial spherically shaped netting layers 220 a through 220 e that are used to protect an asset 150 (such as the International Space Station). In this embodiment, the spacecraft 110 positions the partial spherically shaped netting layers 220 a through 220 e to protect the asset from debris 106. Hence, the orbital removal assembly 100 in this configuration can be used in situations where known orbital information from the NASA office of Orbital Debris tracks debris heading towards the asset 150. The orbital debris removal assembly 100 can then be moved to intercept the debris 106 as illustrated in FIG. 4 before it hits the asset 150.

Referring to FIG. 5, an illustration of three layers of the netting 220 a, 220 b and 220 c is illustrated. In this illustration, fibers 230 make up the first layer of netting 220 a and fiber 240 make up the second layer of netting 220 b and fibers 244 make up the third layer of netting 220 c. As FIG. 5 illustrates, the fibers 230, 240, and 244 have different thicknesses. In particular, fibers 230 that would be on the first layer of netting 220 a are thicker than the fibers 240 in the second layer of netting 220 b which in turn are thicker than the fibers 244 in the third layer of netting 220 c. Each fiber wire thickness is sized to ensure the breakup of incident particles into smaller particles. For example, fiber wire thickness used for composite fiber embodiments is in the range of 0.03 to 0.25 cm. Also illustrated in FIG. 5 is that the fibers 230, 240 and 244 have a different netting density. In particular, fibers 230 in the first layer of 220 a have less fiber mesh density than the fibers 240 in the second layer 220 b which in turn is less dense than the fiber netting 244 in the third layer of netting 220 c. The fiber mesh density (or mesh spacing) in each shell layer is designed to insure that all particles of interest will intersect at least one of the outer shell layers 220 a, 220 b, etc., in a least three locations and the resulting smaller particles will intersect with inner shell layers 220 b through 220 e. Examples, of ranges of mesh spacing would be 0.07 to 0.70 cm and mass densities for composite fibers include 0.9 to 1.5 g/cm̂3. In one embodiment that uses composite fibers, a wire/particle ratio of approximately 0.025 is used to insure the breakup of incident particles into smaller particles. As discussed above, the fibers 230, 240, and 244 in some embodiments are composite fibers. Examples of composite fibers that could be used include, but are not limited to, para-aramid synthetic fibers such as Dyneema and Spectra, polyolefin and ceramic. In another embodiment, wires are used to form the layers of netting. The spacing between netting layers 220 a through 220 e in one embodiment are in the 0.30 to 1 m range. In further one embodiment, the netting layers 220 a through 220 e are spaced 10's to 100's of centimeters apart. In one embodiment the layers 220 a through 220 e are evenly spaced. In another embodiment the spacing is varied.

FIG. 6 illustrates how embodiments of the present invention interact with debris 106. In particular, FIG. 6 illustrates the first layer of netting 220 a, the second layer of netting 220 b, the third layer of netting 220 c, the fourth layer of netting 220 d, and the fifth layer of netting 220 e. Depending on the speed of the debris and what the debris is made of, the impact of the debris on a layer of netting 220 a through 220 e will melt, vaporize or fragment. FIG. 6 illustrates the debris fragmenting on the netting layers 220 a through 220 e. As illustrated, some high velocity debris particles 106 are broken up on impact upon the first outer layer of the netting 220 a. In particular, FIG. 6 illustrates debris particle 106 a impacting the first layer of netting 220 a and a small particle breaking off. Besides breaking off larger particles, the layers of netting 220 a-220 e work to deflect the direction of resulting particles. Debris particles that pass through the first layer of netting 220 a are illustrated passing through space between the first layer of netting 220 a and the second layer of netting 220 b. As illustrated, these particles are smaller in size and travel in a more arbitrary direction because of deflections. In fact, some of the particles will start colliding with each other to produce even smaller particles. As the particles or debris collide with subsequent layers of netting 220 b, 220 c, 220 d, 220 e further break down in the particle size is accomplished. Moreover, as the particles traverse through the layers of netting 220 a, 220 b, 220 c, 220 d and 220 e the randomness of their traveling direction is increased such that an increase in particle to particle collisions between the layer netting is increased. For example, particles traveling between layers 220 b and 220 c are smaller than the particles between the first layer of netting 220 a and 220 b and are traveling in more random directions due to deflections off the respective layers of netting. Further, particles of debris in between layers of netting 220 c and 220 d are smaller still than the particles in-between layers of netting of 220 b and 220 c. Moreover, their direction of travel is even more random causing even more collisions between particles. Further yet, particles between layers of netting 220 d and 220 e are even smaller than particles between 220 c and 220 d. Moreover, their travel of direction is still further more random than the particles in subsequent areas between layers as discussed above. Hence, embodiments of the orbital debris removal assembly 100 provide a mass fission effect such that the particles energies cause the particles to work on themselves to break up to even more smaller particles until only small shield-able debris 106 b (≦2 mm) escapes from the orbital debris removal assembly 100.

In some embodiments, each layer of netting 220 a through 220 e is made of a plurality of sub-layers of meshed fiber netting. For example, referring to FIG. 7, layer 220 a is shown as being made up of sub-layers 250 a through 250 c, layer 220 b is shown as being made up of sub-layers 252 a through 252 c and layer 220 e is shown as being made up of sub-layers 254 a through 254 c. The number of sub-layers per layer can vary depending on the application and desired outcome. In one embodiment 3 to 10 sub-layers are used per layer.

Further in one embodiment, the sub-layers are coupled together with connecting fibers 251. An example illustration of this is illustrated in FIG. 8. As the example illustration of FIG. 8 shows, sub-layers (generally designated as 250) of a layer (generally designated as 220) are coupled together by connecting fibers (generally designated as 251). In this example illustration, each sub-layer 250 comprises an in-plane netting arrangement of meshed fibers that are connected to adjacent sub-layers 250 with a connecting fibers 251. If the orbital debris removal assembly 100 is in the shape of at least a partial sphere, the connecting fibers 251, in one embodiment, are connected to each associated sub-layer 250 in a radially extending configuration. The connection fibers 251 not only tie the sub-layers 250 together but also provide a contact surface for which incoming debris can interact with as the debris penetrates the shield. Although, the sub-layers 250 are shown in FIG. 8 as being spaced from each other for illustration purposes, in some embodiments adjacent sub-layers are in contact with each other.

In one embodiment, the sub-layers 250 in a layer 220 have fibers with uniform fiber thickness, uniform netting spacing (netting density) and fiber alignment as illustrated in FIG. 8. In another embodiment the sub-layers 250 a through 250 c, 252 a through 252 c and 254 a through 254 c can vary in fiber thickness and netting spacing. For example, in FIG. 9, an illustration of some sub-layers 250 a through 250 c of layer 220 a is illustrated. As FIG. 9 illustrates, the fibers 260 that make up the netting of the first sub-layer 250 a have a different thickness and netting spacing than the fibers 262 that make up the second sub-layer 250 b which in turn have a different thickness and netting spacing then the fibers that make up the third sub-layer 250 c.

Although specific embodiments have been illustrated and described herein, it will be appreciated by those of ordinary skill in the art that any arrangement, which is calculated to achieve the same purpose, may be substituted for the specific embodiment shown. For example, the embodiments described above are generally described as being constructed to deal with debris in the range of 0.3 cm to 10 cm. However, the invention can be used to deal with larger or smaller debris with the above described component sizes being modified accordingly. This application is intended to cover any adaptations or variations of the present invention. Therefore, it is manifestly intended that this invention be limited only by the claims and the equivalents thereof. 

1. An orbital debris removal and asset protection assembly comprising: a plurality of spaced layers of netting, each netting layer including sub-layers of meshed composite fibers configured and arranged to break up debris that comes in contact with the assembly.
 2. The orbital debris removal and asset protection assembly of claim 1, further comprising: each spaced layer having a fiber mesh density, the fiber mesh density of one layer of the plurality of spaced layers having a different fiber mesh density of at least one other layer of the plurality of spaced layers.
 3. The orbital debris removal and asset protection assembly of claim 1, further comprising: the composite fibers that make up the meshed fibers have a select thickness, the thickness of the composited fibers of one layer of the plurality of spaced layers being different than the thickness of the fibers in at least one other layer of the plurality of spaced layers.
 4. The orbital debris removal and asset protection assembly of claim 1, further comprising; the plurality of spaced layers of netting at least partially being in a sphere shape.
 5. The orbital debris removal and asset protection assembly of claim 1, further comprising: frame members configured and arranged to hold to the plurality of spaced layers of netting.
 6. The orbital debris removal and asset protection assembly of claim 5, wherein the frame members are configured and arranged to be folded up to put the orbital debris removal assembly in a stowed position.
 7. The orbital debris removal and asset protection assembly of claim 1, wherein the composite fibers are at least one of para-aramid, polyolefin, ceramic and Dyneema fiber bundles.
 8. The orbital debris removal and asset protection assembly of claim 1, further comprising: a spacecraft coupled to the plurality of spaced layers of netting.
 9. The orbital debris removal and asset protection assembly of claim 8, further comprising: at least one deployable boom coupled to the spacecraft; and at least one thruster coupled to the rotational boom to selectively position the spacecraft.
 10. The orbital debris removal and asset protection assembly of claim 8, further comprising: the spacecraft further configured to selectively deploy the plurality of spaced layers of netting and store the plurality of spaced layers of netting.
 11. An orbital debris removal and asset protection assembly comprising: a spacecraft configured to navigate in space; and a plurality of spaced netting layers coupled to the spacecraft, each netting layer including meshed fibers.
 12. The orbital debris removal and asset protection assembly of claim 11, wherein the meshed fibers are composite fibers.
 13. The orbital debris removal and asset protection assembly of claim 11, further comprising: frame members coupled to the spacecraft, the frame member further configured and arranged to form the plurality of the spaced netting layers.
 14. The orbital debris removal and asset protection assembly of claim 13, wherein the frame members foini the spaced netting layers in at least a partial sphere shape.
 15. The orbital debris removal and asset protection assembly of claim 11, further comprising: the plurality of spaced netting layers having an outer layer, an inner layer and at least one mid layer between the outer layer and the inner layer, each layer having a select fiber mesh density, the fiber density of the meshed fibers in each spaced layer increasing from the outer layer to the inner layer.
 16. The orbital debris removal and asset protection assembly of claim 11, further comprising: the plurality of spaced netting layers having an outer layer, an inner layer and at least one mid layer between the outer layer and the inner layer; and the meshed fibers in each layer having a select thickness, the thickness of the meshed fibers in each spaced layer decreasing from the outer layer to the inner layer.
 17. The orbital debris removal and asset protection assembly of claim 11, wherein each netting layer, includes a plurality of sub-layers of meshed fibers.
 18. The orbital debris removal and asset protection assembly of claim 17, further comprising: a plurality of connecting fibers configured and arranged to couple the sub-layers together.
 19. The orbital debris removal assembly and asset protection assembly of claim 17, wherein at least one sub-layer of the plurality of sub-layers has a different fiber spacing than at least one other sub-layer.
 20. The orbital debris removal assembly and asset protection assembly of claim 17, wherein at least one sub-layer of the plurality of sub-layers has a different fiber thickness than at least one other sub-layer.
 21. An orbital debris removal and asset protection assembly comprising: a plurality of spaced layers of netting formed in at least a partial sphere shape, each netting layer including meshed composite fibers, the plurality of spaced layers of netting having an outer layer, an inner layer and at least one mid layer between the outer layer and the inner layer, each layer having a select fiber density, the fiber density of the meshed composite fibers in each spaced layer varying from the outer layer to the inner layer.
 22. The orbital debris removal and asset protection assembly of claim 21, further comprising: a spacecraft coupled to the plurality of spaced layers; at least one deployable boom coupled to the space craft; and at least one thruster coupled to the deployable boom to selectively position the spacecraft at a desired location in space.
 23. The orbital debris removal and asset protection assembly of claim 21, the plurality of spaced layers of netting having a first section and a second section, the first and section conformed and arranged to form a complete sphere when deployed.
 24. The orbital debris removal and asset protection assembly of claim 21, wherein the meshed composite fibers in each layer have a select thickness, the thickness of the meshed fibers in each spaced layer decreasing from the outer layer to the inner layer.
 25. The orbital debris removal and asset protection assembly of claim 21, further comprising: a plurality of frame members configured and arranged to selectively space the plurality spaced layers of netting.
 26. The orbital debris removal and asset protection assembly of claim 25, wherein the frame members are further configured to place the plurality of spaced layers of netting in a deployed position and a storage position.
 27. The orbital debris removal and asset protection assembly of claim 25, further comprising: at least one deployable member configured to selectively deploy the plurality of spaced layers of netting.
 28. The orbital debris removal and asset protection assembly of claim 22, further comprising: a controller configured to control the thrusters of the spacecraft; a transceiver in communication with the controller to provided communications to the controller; and at least one sensor in communication with the controller.
 29. The orbital debris removal and asset protection assembly of claim 28, wherein the at least one sensor is at least one of an impact sensor and a velocity sensor.
 30. The orbital debris removal and asset protection assembly of claim 21, wherein at least one of the plurality of spaced layers is made of a plurality of meshed composite fiber sub-layers. 